Method for managing heat exchange between fluids e.g. fuel, in turbomachine e.g. dual flow gas turbine engine of airplane, involves adjusting thermal transfer towards fuel to obtain temperature of fuel injected into combustion chamber

摘要

The method involves providing information representing temperature (Ti) of fuel that is injected into a combustion chamber (1) via injectors (26), and adjusting thermal transfer towards the fuel to obtain the temperature of the fuel injected into the combustion chamber within a limit of a predetermined set point for any operating range of a turbomachine, where the adjustment of the thermal transfer is carried out by adjustment of distribution of oil flow between a fraction traversing an oil/air heat exchanger (32) and a complementary fraction obtained from the exchanger. An independent claim is also included for a system for managing heat exchange between fluids in a turbomachine of an airplane, comprising a fuel system.